**4.4 Laminar flow past a delta wing**

A laminar flow at a high angle of attack past a delta wing is considered here. The free-stream Mach number is of *<sup>M</sup>*<sup>∞</sup> <sup>¼</sup> <sup>0</sup>*:*3, the angle of attack is of *<sup>α</sup>* <sup>¼</sup> <sup>12</sup>*:*5*<sup>o</sup>* , and the Reynolds number is of Re ¼ 4,000 based on a mean cord length of 1. The triangular

**Figure 4.** *Vorticity magnitude contours and for laminar past a sphere at Re* <sup>∞</sup> ¼ 100.

**Figure 5.** *Pressure coefficient for laminar past a sphere, compared to ref. [22].*

meshes of the symmetric plane and the delta wing surface are shown in **Figures 6** and **7**. Characteristic condition is given at the upper, lower, left, and right boundaries in **Figure 6**. The adiabatic wall boundary condition is given at the wing surface, where the heat transfer through the wall is zero, and no mass or total energy convection is supposed. The computed vorticity magnitude contours are shown in **Figure 8** along with the stream traces in the flow field. It is observed that as the flow passes the leading edge, it rolls up and creates a vortex. The vortex system remains over a distance behind the wing.
